US5343696A - Thrust reverser for a propfan engine - Google Patents

Thrust reverser for a propfan engine Download PDF

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Publication number
US5343696A
US5343696A US08/075,510 US7551093A US5343696A US 5343696 A US5343696 A US 5343696A US 7551093 A US7551093 A US 7551093A US 5343696 A US5343696 A US 5343696A
Authority
US
United States
Prior art keywords
shroud
nozzle ring
engine according
engine
flaps
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US08/075,510
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English (en)
Inventor
Alois Rohra
Peter Tracksdorf
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
Rolls Royce Solutions GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Assigned to MTU MOTOREN-UND TURBINEN-UNION reassignment MTU MOTOREN-UND TURBINEN-UNION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ROHRA, ALOIS, TRACKSDORF, PETER
Application granted granted Critical
Publication of US5343696A publication Critical patent/US5343696A/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/68—Reversers mounted on the engine housing downstream of the fan exhaust section

Definitions

  • the invention relates to a propfan or propeller engine having a shroud which surrounds the propfan or propeller and, more particularly, to a shroud having a variable geometry.
  • the direction of the flow inside the shroud duct is reversible for the reversal of the thrust by adjustable fan blades or propeller blades.
  • the invention relates to so-called "UHB-aircraft engines" (Ultra-High-Bypass), thus, the invention relates to engines with a very high bypass ratio, for example, on the order of 10:1.
  • a typical engine of this category has two shrouded contra-rotating propfan rotors.
  • the blades of the propfan rotors are constructed to be adjustable in their pitch. Furthermore, by a corresponding rotor blade adjustment, a surging of the compressor is avoided.
  • German Patent Document DE-OS 24 46 548 discloses moving the blades of a fan or of a propfan in the reverse position. In this case, the air for generating a reverse thrust is taken in around the trailing edge of the shroud and is blown out inside the shroud duct toward the front in the flight direction.
  • the flaps which are pivotally connected to the outlet of the shroud are swivelled out in such a manner that they form a bell-shaped inlet opening.
  • the resulting enlarged inlet cross-section has the purpose of causing an improved flow through the fan and thus a larger reverse thrust.
  • a burbling in the case of the flow around the sharp trailing edge of the flap with the connected impairment of the thrust reversing effect cannot be prevented or limited.
  • the turbulent flow against the rotor blades caused by the burbling may result in a dangerous excitation of vibrations of the rotor blades.
  • the displaceable nozzle ring for the thrust reversal position, is to be moved axially into a ring-shaped pocket of the shroud.
  • This embodiment is distinguished by its simple and light construction. The servicing expenditures remain low because the nozzle ring is formed of one component. This ensures considerable reliability.
  • the nozzle ring is composed of several ring segments. It is therefore possible to displace the ring segments with respect to the stationary shroud by swivelling levers axially forward and radially so far toward the outside that the trailing edges of the ring segments form, with the trailing edge of the stationary shroud, an edge of greater radial cross section which promotes the surrounding flow.
  • the higher air resistance of the shroud when the ring segments are moved out proves to be advantageous without any significant increase of the maximal diameter which would reduce the ground clearance in the case of wing-mounted engines.
  • the rearward end of the shroud is constructed as a movable nozzle ring divided into separate ring segments.
  • the individual ring segments by means of their swivelling levers, can be moved axially forward and radially toward the outside as well as while turning about their body axis which is situated perpendicularly with respect to the translatory moving plane.
  • the ring segments can be moved into such a position that, in their moved-out end position, they assume a position which is offset from the rearward end of the stationary shroud and adjusted with respect to the outer air flow.
  • the trailing edge of the respective ring segment points to the core housing.
  • the interior side of the ring segments forms flow ducts with the exterior side of the shroud.
  • the flow ducts guide the air flow in an aerodynamically advantageous manner around the rearward end of the shroud.
  • swivelling flaps are arranged in sections on the circumference of the shroud, which flaps, in the moved-out condition not only promote the flow around the rearward shroud end but also the face of the engine and thus increase the braking effect.
  • the cause of the favorable surrounding flow is the separating whirl which is generated on the rearward edge of the flap and which has a rounding-off effect for the rearward shroud end. The surrounding flow therefore takes place in a larger radius in which case the risk of burbling is reduced.
  • the flaps are coupled with the nozzle ring in such a manner that their movement takes place simultaneously. As a result, an optimal flow-around quality is ensured.
  • the shroud duct which is formed between the core housing, on the one hand, and the interior side of the shroud with the nozzle ring, on the other hand, extends in a divergent manner, that is, forward, in the flow direction during the thrust reversal.
  • the inlet cross-section will increase and the flow losses will therefore be reduced.
  • the flow losses are a function of the expansion ratio of the shroud duct and of the flow Mach number at the inlet.
  • an effective function of the thrust reverser is indicated while the blades are adjusted at the same time as the nozzle ring is displaced.
  • FIG. 1 is a longitudinal sectional view of a propfan engine with a one-piece nozzle ring in the flying condition;
  • FIG. 2 is a propfan engine according to FIG. 1 during the thrust reversing operation
  • FIG. 3 is an perspective overall view of the propfan engine in the flying condition according to FIG. 1;
  • FIG. 4 is a view of the propfan engine according to FIG. 3 during the thrust reversing operation
  • FIG. 5 is a longitudinal sectional view of the rear area of the shroud with the nozzle ring and the flaps in the flying condition;
  • FIG. 6 is a view of the shroud nozzle according to FIG. 5 with the nozzle ring and the flaps situated in the thrust reversing position;
  • FIG. 7 is an overall view of the shroud according to FIG. 6;
  • FIG. 8 is a longitudinal sectional view of a propfan engine with a nozzle ring which consists of ring segments, in the flying condition;
  • FIG. 9 is a view of the propfan engine according to FIG. 8 with ring segments which are in the thrust reversing position;
  • FIG. 10 is a view of an alternative embodiment of the propfan engine according to FIG. 8.
  • FIG. 11 is a view of the propfan engine according to FIG. 9 with ring segments which are swivelled out for the guiding of air.
  • FIG. 1 is an axial sectional view of a propfan engine for the propulsion of an aircraft.
  • the propfan engine consists essentially of the two propfan rotors 1, having rotor blades 3, which are situated inside the shroud 2 of an interior gas turbine which is not shown in detail.
  • a nozzle ring 4 closes off the shroud 2. As illustrated in FIG. 1, the air flow passes from the front to the rear through the shroud duct M, for example, during cruising. In this case, the nozzle ring 4 is in the moved-out position.
  • the rotor blades 3 and the nozzle ring 4 are moved into the thrust reversal position at the same time as illustrated in FIG. 2.
  • the air flow S flows around the trailing edges of the shroud 2 before it flows through the shroud duct M toward the front of the engine.
  • FIGS. 3 and 4 are perspective views of the flight or thrust reversal position of the nozzle ring 4.
  • FIGS. 5-7 in an alternative construction, for improving the surrounding flow in the thrust reversal operation, flaps 5 are actuated at the same time as the nozzle ring 4.
  • the flaps 5 swivel about a swivel axes 9 toward the outside.
  • the actuating takes place by way of a link which is situated in the flap 5 and in which a roller 9a is arranged.
  • the roller 9a rolls along the link.
  • the roller 9a is disposed on the ring segment 6 (see FIGS. 8 and 9) which moves the link to swivel the flap 5 outward.
  • FIGS. 5 and 6 are longitudinal sectional views of the flight operating position or the thrust reversal position. A perspective view of the propfan engine in the thrust reversal configuration is illustrated in FIG. 7.
  • FIGS. 8 and 9 Another advantageous embodiment is illustrated in the longitudinal sectional views of FIGS. 8 and 9.
  • the ring segments 6 which, in the flying condition, form the nozzle ring 4 according to FIG. 8, for the thrust reversal, are swivelled by a swivelling lever 11 to the exterior side of the rear shroud 2.
  • the ring segments 6 rest in their end position concentrically around the shroud 2.
  • the air flow S will then flow around the exterior side of the ring segments 6 and the stationary end of the shroud 2 according to FIG. 9.
  • the ring segments 6 are moved into a position illustrated in FIG. 11 which forms a flow duct leading the air flow S between the end of the shroud 2 and the interior side of the ring segments 6.
  • FIG. 10 shows the position of the ring segments 6 during the flight.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US08/075,510 1990-12-13 1991-10-29 Thrust reverser for a propfan engine Expired - Fee Related US5343696A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE4039810 1990-12-13
DE4039810A DE4039810C1 (zh) 1990-12-13 1990-12-13
PCT/EP1991/002040 WO1992010660A1 (de) 1990-12-13 1991-10-29 Schubumkehrvorrichtung für ein propfantriebwerk

Publications (1)

Publication Number Publication Date
US5343696A true US5343696A (en) 1994-09-06

Family

ID=6420234

Family Applications (1)

Application Number Title Priority Date Filing Date
US08/075,510 Expired - Fee Related US5343696A (en) 1990-12-13 1991-10-29 Thrust reverser for a propfan engine

Country Status (7)

Country Link
US (1) US5343696A (zh)
EP (1) EP0561791B1 (zh)
JP (1) JPH06505781A (zh)
DE (2) DE4039810C1 (zh)
ES (1) ES2060407T3 (zh)
RU (1) RU2094639C1 (zh)
WO (1) WO1992010660A1 (zh)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996009206A1 (en) * 1994-09-19 1996-03-28 Lockheed Corporation A shroud for a reversible thrust fan
US5722231A (en) * 1995-07-26 1998-03-03 Aerospatiale Societe Nationale Industrielle Turbofan with thrust reversal doors not submitted to bypass air in their inactive position
US5730392A (en) * 1995-09-22 1998-03-24 Aeronautical Concept Of Exhaust, Ltd. Adjustable fairing for thrust reversers
US5974783A (en) * 1996-12-26 1999-11-02 Societe Hispano-Suiza Turbojet engine thrust reverser having movable rear baffle pivattally connected by forward and rear linkrods which are totally enclosed in the forward thrust mode
US20030159430A1 (en) * 2001-04-26 2003-08-28 Jean-Pierre Lair Thrust vectoring and variable exhaust area for jet engine nozzle
US20040067383A1 (en) * 2000-12-18 2004-04-08 3M Innovative Properties Company Dental mill blank assembly
US20080121756A1 (en) * 2006-11-24 2008-05-29 The Boeing Company Unconventional Integrated Propulsion Systems and Methods for Blended Wing Body Aircraft
US20080163606A1 (en) * 2007-01-08 2008-07-10 United Technologies Corporation Variable area nozzle with woven sleeve extension
US8127532B2 (en) 2008-11-26 2012-03-06 The Boeing Company Pivoting fan nozzle nacelle
US20140230403A1 (en) * 2012-01-31 2014-08-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US8959889B2 (en) 2008-11-26 2015-02-24 The Boeing Company Method of varying a fan duct nozzle throat area of a gas turbine engine
US9194329B2 (en) 2012-01-31 2015-11-24 United Technologies Corporation Gas turbine engine shaft bearing configuration
EP3023623A1 (en) * 2014-11-21 2016-05-25 General Electric Company Gas turbine engine with thrust reversal and method of assembling the same
FR3052191A1 (fr) * 2016-06-01 2017-12-08 Snecma Inversion de poussee dans une turbomachine avec soufflante a calage variable
US10113508B2 (en) 2014-11-21 2018-10-30 General Electric Company Gas turbine engine and method of assembling the same
US10288075B2 (en) 2016-03-24 2019-05-14 Toyota Jidosha Kabushiki Kaisha Thrust generating apparatus for controlling attitude of movable body
US10502160B2 (en) 2016-02-09 2019-12-10 General Electric Company Reverse thrust engine
WO2019234371A1 (fr) * 2018-06-07 2019-12-12 Safran Ensemble de propulsion pour un aeronef a decollage et atterrissage verticaux
US11401831B2 (en) 2012-01-31 2022-08-02 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2766522B1 (fr) * 1997-07-24 1999-09-03 Hispano Suiza Sa Inverseur de poussee de turbosoufflante a obstacle a guidage axial lies au capot primaire
DE10041619A1 (de) 2000-05-22 2001-11-29 Bayer Ag Selektive Herbizide auf Basis von Heteroaryloxyacetamiden
DE10146591A1 (de) 2001-09-21 2003-04-10 Bayer Cropscience Ag Herbizide auf Basis von substituierten Thien-3-yl-sulfonylamino(thio)carbonyl-triazolin(thi)onen
DE102004010813A1 (de) 2004-03-05 2005-11-10 Bayer Cropscience Ag Neue Herbizide auf Basis von substituierten Thien-3-yl-sulfonylamino(thio)carbonyltriazolin(thi)onen und 4-HPPD-Hemmstoffen
FR2958910B1 (fr) * 2010-04-20 2012-04-27 Aircelle Sa Nacelle pour moteur d'aeronef a tuyere de section variable
PL417832A1 (pl) * 2016-07-04 2018-01-15 General Electric Company Zespół rozszerzenia kielichowego, zwłaszcza do dyszy i sposób jego rozkładania oraz silnik turbowentylatorowy zawierający ten zespół
US11053888B2 (en) * 2017-11-01 2021-07-06 The Boeing Company Fan cowl with a serrated trailing edge providing attached flow in reverse thrust mode
PL235797B1 (pl) * 2018-02-21 2020-10-19 Gen Electric Zespół dyszy dzwonowej do silników turbogazowych oraz sposób odwracania ciągu silnika turbowentylatorowego

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2570629A (en) * 1945-10-05 1951-10-09 Anxionnaz Adjustable pipe for the intake of air and expansion of the driving gases in reactionjet propellers for projectiles and vehicles
GB861819A (en) * 1957-07-29 1961-03-01 Boeing Co Noise suppressor and thrust reverser for jet propulsion engines
DE2446548A1 (de) * 1973-10-11 1975-04-17 United Aircraft Corp Triebwerk mit ummanteltem geblaese
GB1565212A (en) * 1975-12-22 1980-04-16 British Hovercraft Corp Ltd Ductecd fan propulsors
GB2070691A (en) * 1980-01-11 1981-09-09 Rolls Royce Radial splitter for reversible pitch fan propulsion unit.
US4802629A (en) * 1982-10-22 1989-02-07 The Boeing Company Plug-type exhaust nozzle having a variable centerbody and translating shroud

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2570629A (en) * 1945-10-05 1951-10-09 Anxionnaz Adjustable pipe for the intake of air and expansion of the driving gases in reactionjet propellers for projectiles and vehicles
GB861819A (en) * 1957-07-29 1961-03-01 Boeing Co Noise suppressor and thrust reverser for jet propulsion engines
DE2446548A1 (de) * 1973-10-11 1975-04-17 United Aircraft Corp Triebwerk mit ummanteltem geblaese
GB1565212A (en) * 1975-12-22 1980-04-16 British Hovercraft Corp Ltd Ductecd fan propulsors
GB2070691A (en) * 1980-01-11 1981-09-09 Rolls Royce Radial splitter for reversible pitch fan propulsion unit.
US4802629A (en) * 1982-10-22 1989-02-07 The Boeing Company Plug-type exhaust nozzle having a variable centerbody and translating shroud

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996009206A1 (en) * 1994-09-19 1996-03-28 Lockheed Corporation A shroud for a reversible thrust fan
US5516061A (en) * 1994-09-19 1996-05-14 Lockheed Corporation Shroud for a reversible thrust fan
US5722231A (en) * 1995-07-26 1998-03-03 Aerospatiale Societe Nationale Industrielle Turbofan with thrust reversal doors not submitted to bypass air in their inactive position
US5730392A (en) * 1995-09-22 1998-03-24 Aeronautical Concept Of Exhaust, Ltd. Adjustable fairing for thrust reversers
US5974783A (en) * 1996-12-26 1999-11-02 Societe Hispano-Suiza Turbojet engine thrust reverser having movable rear baffle pivattally connected by forward and rear linkrods which are totally enclosed in the forward thrust mode
US20040067383A1 (en) * 2000-12-18 2004-04-08 3M Innovative Properties Company Dental mill blank assembly
US20030159430A1 (en) * 2001-04-26 2003-08-28 Jean-Pierre Lair Thrust vectoring and variable exhaust area for jet engine nozzle
US6938408B2 (en) 2001-04-26 2005-09-06 Propulsion Vectoring, L.P. Thrust vectoring and variable exhaust area for jet engine nozzle
US20080121756A1 (en) * 2006-11-24 2008-05-29 The Boeing Company Unconventional Integrated Propulsion Systems and Methods for Blended Wing Body Aircraft
US7665689B2 (en) * 2006-11-24 2010-02-23 The Boeing Company Unconventional integrated propulsion systems and methods for blended wing body aircraft
US20080163606A1 (en) * 2007-01-08 2008-07-10 United Technologies Corporation Variable area nozzle with woven sleeve extension
EP1944496A2 (en) * 2007-01-08 2008-07-16 United Technologies Corporation Variable area nozzle with woven sleeve extension
US7966828B2 (en) * 2007-01-08 2011-06-28 United Technologies Corporation Variable area nozzle with woven sleeve extension
EP1944496A3 (en) * 2007-01-08 2011-10-19 United Technologies Corporation Variable area nozzle with woven sleeve extension
US8959889B2 (en) 2008-11-26 2015-02-24 The Boeing Company Method of varying a fan duct nozzle throat area of a gas turbine engine
US8127532B2 (en) 2008-11-26 2012-03-06 The Boeing Company Pivoting fan nozzle nacelle
US10215094B2 (en) 2012-01-31 2019-02-26 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9194329B2 (en) 2012-01-31 2015-11-24 United Technologies Corporation Gas turbine engine shaft bearing configuration
US11401831B2 (en) 2012-01-31 2022-08-02 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US11486269B2 (en) 2012-01-31 2022-11-01 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US10400629B2 (en) * 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US11566586B2 (en) 2012-01-31 2023-01-31 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US20140230403A1 (en) * 2012-01-31 2014-08-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US11149689B2 (en) 2012-01-31 2021-10-19 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US10113508B2 (en) 2014-11-21 2018-10-30 General Electric Company Gas turbine engine and method of assembling the same
CN105626310B (zh) * 2014-11-21 2017-12-22 通用电气公司 燃气涡轮发动机及组装其的方法
JP2016098820A (ja) * 2014-11-21 2016-05-30 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン及びその組み立て方法
US10465538B2 (en) 2014-11-21 2019-11-05 General Electric Company Gas turbine engine with reversible fan
US20160146113A1 (en) * 2014-11-21 2016-05-26 General Electric Company Gas turbine engine and method of assembling the same
EP3023623A1 (en) * 2014-11-21 2016-05-25 General Electric Company Gas turbine engine with thrust reversal and method of assembling the same
US10502160B2 (en) 2016-02-09 2019-12-10 General Electric Company Reverse thrust engine
US10288075B2 (en) 2016-03-24 2019-05-14 Toyota Jidosha Kabushiki Kaisha Thrust generating apparatus for controlling attitude of movable body
FR3052191A1 (fr) * 2016-06-01 2017-12-08 Snecma Inversion de poussee dans une turbomachine avec soufflante a calage variable
FR3082186A1 (fr) * 2018-06-07 2019-12-13 Safran Ensemble de propulsion pour un aeronef a decollage et atterrissage verticaux
WO2019234371A1 (fr) * 2018-06-07 2019-12-12 Safran Ensemble de propulsion pour un aeronef a decollage et atterrissage verticaux

Also Published As

Publication number Publication date
EP0561791B1 (de) 1994-08-17
DE4039810C1 (zh) 1991-10-17
WO1992010660A1 (de) 1992-06-25
DE59102584D1 (de) 1994-09-22
EP0561791A1 (en) 1993-09-29
RU2094639C1 (ru) 1997-10-27
ES2060407T3 (es) 1994-11-16
JPH06505781A (ja) 1994-06-30

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